Method for producing a run-in coating, a run-in system, a turbomachine, as well as a guide vane

1. A method for producing a run-in coating for a turbomachine for braking a rotor in the event of a shaft breakage, comprising:

forming the run-in coating as an integral blade portion during a generative manufacture of a blade, wherein the generative manufacture includes forming the blade and the run-in coating through deposition and melting of metal powder in layers.

2. The method as recited in claim 1 further comprising constructing a generative structure during manufacture of the blade and removing the structure following the manufacture of the blade.

3. The method of claim 1 , wherein the run-in coating forms an abradable ring, and the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps which together form an integral, closed or open abradable ring having a chamber-type material structure.

4. The method of claim 1 , wherein each run-in coating includes a damping layer for shock absorption and a braking layer for optimizing braking.

5. A run-in system comprising an integral, closed or open abradable ring including a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the run-in coatings forming the abradable ring extending over a rotor blade row and located axially between outer shrouds of the rotor blade row and outer shrouds of a guide vane row and having a chamber-type material structure.

6. The run-in system as recited in claim 5 wherein the abradable ring is formed either on a side of the outer shrouds of the rotor blade row opposite a side of the outer shrouds of the guide vane row, or on a side of the outer shroud of the guide blade row opposite a side of the outer shroud of the rotor vane row.

7. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading sides of outer shrouds of the guide vane row.

8. The run-in system as recited in claim 5 wherein the abradable ring is placeable on leading edges of guide vanes.

9. The run-in system as recited in claim 5 wherein an abrasive ring is configurable for running onto the abradable ring of trailing sides of outer shrouds of the rotor blade row in response to a shaft breakage.

10. The run-in system as recited in claim 5 wherein the run-in coatings are manufactured in accordance with the method recited in claim 1 .

11. A turbomachine comprising the run-in system as recited in claim 5 , and an abrasive ring for running onto the abradable ring in response to a shaft breakage,

the abradable ring being disposed in the leading region of the guide vane row, and the abrasive ring being formed in the upstream trailing region of a rotor blade row opposite the abradable ring.

12. A guide vane row comprising

a plurality of guide vanes, each guide vane including an outer shroud and an inner shroud; and

an abradable ring in a leading region of the guide vane, wherein the abradable ring includes a plurality of run-in coatings mutually laterally spaced apart by circumferential gaps along the circumference of the abradable ring, the plurality of run-in coatings having a chamber-type material structure.

13. The guide vane as recited in claim 12 wherein the run-in coatings are formed on a leading side of the outer shrouds.

14. The guide vane as recited in claim 12 wherein the run-in coatings are formed radially outwardly on a leading edge of a blades of each guide vane.

15. The guide vane as recited in claim 12 wherein the run-in coatings are formed on an edge portion of a leading edge displaced upstream relative to a radially inner edge portion of each guide vane.